Underwater weapon



April 11, 1967 A. T. BlEHL ETAL 3,313,207

UNDERWATER WEAPON Original Filed April 2, 1965 2 Sheets-Sheet 2 13E 141INVENTORS 14, ARTHUR T. BIEHL ROBERT MAIN HARDT FICLYEL 2 ATTORNEYUnited States Patent 7 Claims. (Cl. 89-1.813)

This application is a divisional application of my copending applicationSer. No. 445,277, filed Apr. 2, 1965, entitled, Underwater Weapon, whichis a continuationin-part of application Ser. No. 225,672, filed Sept.24, 1962, entitled, Underwater Weapon, the latter application nowabandoned.

The present invention relates in general to the field of underwaterweapons and more particularly to a hand held underwater weapon whereinsmall rockets embodying novel construction features are employed toobtained unusual underwater ordnance efiects.

Heretofore, hand held underwater weapons for fishing as well as formilitary applications have consisted of arbalete, spring driven,compressed gas, and explosive drive guns, all of which have certaindisadvantages. Not the least of these disadvantages are that theseweapons have relatively short range and very low penetrating power.Moreover, they are complicated to fire and hard to reload. Some of theadvantages which could be obtained by using the underwater weaponcomprising a rocket projectile are apparent from experience with largerrockets. Among these would be the elimination of recoil and muzzleblast, both of which are very undesirable underwater. Simplification ofthe design can be accomplishedthrough the reduction of the need forprecision manufacturing of launching apparatus, and reduction of theoverall size and weight of the weapon. The cost is comparable, and inmost cases less, than previously existing weapons.

In accordance with the present invention the launcher housing, launchtubes, and rockets may be made entirely of a strong plastic ornon-magnetic material so as not to interfere with the operators compass,i.e., his navigation. A rocket propelled projectile also has a decidedadvantage over spring or arbalete projectiles in that it attains itsmaximum velocity at same distance from the launcher whereby theprojectiles have the greatest energy in the target area. Although somecompressed gas projectiles may exhibit this feature, they have a muchlower energy potential wherefore the target range and effectiveness isconsiderably less. Compressed gas weapons also require undesirably heavybulky containers for transporting the gas. The use of a rocketprojectile in underwater applications also affords utilization of thecombustion chamber flame to ignite a tracer as a pyrotechnic delay trainwhich may be used to set off high explosives in a warhead. Impactinitiated warheads are also contemplated and described herein.

In accordance with the present invention some embodiments of the rocketprojectile are reusable, as propellant charges may be replaced therein,allowing the use of the entire casing and nozzle many times.Furthermore, stabilization of these rockets is achieved by a drag orroll induced through the configuration of the rocket nozzle orprojectile exterior design. Normal finned stabilizing techniques couldbe used. The former two techniques obviate the need for fins, whichreduces the complexity and size of the launchers required for theserockets. Novel ignition techniques are also contemplated which providecontrol of the launching sequence, as well as reliable ignition of therocket underwater, and are disclosed herein.

An object of this invention is to provide an underwater 3,313,297Patented Apr. 11, 1967 weapon which is light weight, small, easilyreloadable, inexpensive, and yet attains high energy with deeppenetrating power at long range.

Another object of this invention is to provide an underwater weaponwhich has very little recoil or muzzle blast, and does not produce anunpleasant or unbearable underwater sound effect.

A further object of this invention is to provide a miniature rocket ofnovel construction features which is suitable 1f lor underwateroperation and has a variety of lethal wareads.

A still further object of this invention is to provide a means formaintaining miniature underwater rockets in dynamic stability.

Still another object of this invention is to provide an underwaterweapon comprising reusable rocket projectiles.

Yet another object of this invention is to provide novel ignitiontechniques for underwater operation of small rockets.

Other objects and advantages of this invention will be set forth in thefollowing description of the invention and illustrated in theaccompanying drawings, in which similar reference characters relate tosimilar components and of which drawings:

FIGURE 1 is a side view of one embodiment of the present inventiondepicting the rocket, rocket launcher, and ignition means.

FIGURE 2 is a side view, in section, of a miniature rocket having a timedelay actuated explosive warhead.

FIGURE 3 is a projection of the section taken on lines 33 of FIGURE 2.

FIGURE 4 is a side view, in section, of an underwater rocket propelledunderwater spear.

FIGURES is a projection of the section taken on lines 55 of FIGURE 4.

FIGURE 6 is a side view, in section, of an impact detonating underwaterrocket having a warhead.

FIGURE 7 is a side view, in section, of a different type of warhead.

FIGURE 8 is a side view, partially in section of a simple mechanism forfiring the underwater rockets of the present invention.

FIGURE 9 is a side view, partially in section, of the launcher of FIGURE8 arranged for underwater reloading.

FIGURE 10 is a cross-section taken substantially on line 1010 of FIG. 9with certain parts shown in elevation.

FIGURE 11 is a side view, partially in section, of an alternative meansof providing roll stabilization for the rockets of the presentinvention.

FIGURE 12 is a projection of the section on lines 12-12 of FIGURE 11.

FIGURE 13 is a side, in section, of another alternative means ofproviding roll stabilization for the rockets of the present invention. 7

FIGURE 14 is a projection of the section on lines 14-14 of FIGURE 13.

Referring now to the drawings by reference characters and referringparticularly to FIGURE 1, there shown is a rocket generally designated21 having casing 32 in which propellant 33 is disposed. The casing maybe made of metal such as steel or aluminum or high strength plasticssuch as nylon, phenolic based resin or polystyrene. The casing must beable to withstand the chamber pressures developed inside the rocketwhich are on the order of 500 to 3000 p.s.i. Most materials are suitablefor this if the correct wall thicknesses are selected but the casingmust also be capable of securing a nozzle, being waterproof, and in someinstances being able to withstand high temperatures. The lastrequirement may be overcome by a suitable propellant inhibitor (see US.

patent application Small Arms Weapon, Ser. No. 43 5,780, filed Feb. 11,1965, for suitable inhibitors and propellants). The rocket is alsoprovided with a nozzle 34 in the aft end of the casing to developthrust. It may be formed as an integral part of the casing as shown orit may be made separate and inserted as described herein below. Suitablenozzle materials include most metals such as steels, aluminum, brass andcopper and many plastics including nylon, polystyrene, phenolic basedresins, epoxies, and ceramic materials, the propellant has a cylindricalperforation 36 into which a pyrotechnic fuse 37 is inserted. The space38 allows the passage of exhaust gases through the nozzle orifices. Thediameter of the nozzle and the diameter of the perforation of the grainmust be so designed as to achieve the desired burning characteristics,chamber pressures, and burn rates. This may be done by giving theperforation diameter and nozzle the correct initial magnitudes. Inaddition, the nozzle can be made to ablate commensurately with theincrease in the perforation diameter during burning if the grainperforation is such that it can continually expose a greater surface ofpropellant as the burn progresses and is not a neutral or regressiveperforation. A booster may be located in the perforation diameter alongwith the pyrotechnic fuse and may be simply a loosely packed materialsuch as thermite (Al Fe O The booster material which deflagrates,scattering hot molten slag, insures the ignition of the propellantthroughout the length of the perforation in a rapid and uniform mannerthus allowing the immediate attainment of the desired chamber pressure.

The front portion of the rocket is provided with a warhead 39 whichterminates in the nose 41 and is secured to the rocket casing by a tightpress fit or a mechanical seal. The warhead may be any one of a numberof suitable materials and standard configurations such as barbed ortogglehead which are especially valuable in fishing operations.Additional novel head configurations suitable for use with extremelyhigh performance obtainable from the present invention will be disclosedand claimed hereinafter.

In FIGURE 1 the warhead has a pointed nose and a suitable material wouldbe brass, steel or even tungsten carbide due to their high density whichprovides the proper balance to the projectile. Increased ordnanceeffects might be achieved by making the warhead of the explodingvariety. The warhead contacts the casing along the interface 42 and issecured therein by means of a removable locking pin 43. The pin isprovided as a safety device preventing the rocket from attaining highperformance by having it drag the launching tube, if it is accidentlyignited, or providing an insulated handhold for the operation torestrain the rocket. An ignition means is located in the nozzle whichconsists of a pyrotechnic compound 44 having a wire 46 extendingtherethrough. The wire has a zig-zag end 47 and is coated with apyrotechnic material and in operation is pulled through the compound inthe nozzle. The friction at the zig-zag end with its pyrotechnic coatingas it passes through the pyrotechnic material in the nozzle causes thecombined materials to flash from the nozzle into the space between thenozzle and the propellant grain, and subsequently into the perforation,thus igniting the fuse. The wire is provided with a pulling means whichmay consist of a ring 48 or disc or other suitable structure by whichthe operator can pull the wire.

The rocket is disposed inside a launcher or launch tube 49 which may beof a suitable material such as plastic, metal or impregnated paper. Thelauncher is sealed at both ends by frangible diaphragms 51, 52 whichhave a suitable means for allowing the wire to pass therethrough whilemaintaining water tight characteristics. The aft end 56 of the rocketcasing may be provided with a screw thread thus allowing the warhead tobe removably secured to the casing portion of the rocket which containsthe combustion chamber. With this embodiment it is contemplated that newpropellant grains may be inserted into the casing section and theprojectile used many times, unless of course, the warhead is destroyedby a payload such as high explosive. If the latter is the case, a newwarhead section may be attached to the old casing section if the latteris located after use. Similarly the entire engine section comprising thecasing, nozzle, and propellant may be made as one unit and attached tothe warhead.

FIGURE 2 is a cross section of a rocket suitable for underwater use andhaving a high performance explosive warhead. A substantially tubularcasing 59 having forward 53 and rearward 59 ends is made of metal,generally steel. Bundy lap-welded steel tubing has worked very well. Apointed nose portion 61 is secured in the forward most end of thecasing. It can be held adequately by simply crimping the casing into anannular groove 62 around the nose or by other mechanical engagementmeans such as threads, etc. The nose should be of a heavy metal in orderthat the center of gravity of the rocket be at least 60% of the lengthof the rocket from the rearward end. The nose is pointed forhydrodynamic streamlining and to permit the rocket to penetrate thetarget. If desired, a small high explosive warhead 63 can be used suchas Composition C, compacted pellets of pentaerythritol tetranitrate(PETN), black powder, double base gun powder, or simply the waste fromthe double base propellants produced in manufacturing the propellantgrains of the rockets. An outside inhibited center burning propellantgrain 64 is disposed in the rearward end of the casing. A nozzle means66 is located in the rearward end of the casing adjacent to propellantgrain and is arranged for imparting rotation to the rocket in itsunderwater trajectory. Various nozzle means for accomplishing this willbe described hereinafter.

A novel rocket ignition means for underwater use is located in therearward end of the rocket and uniformly ignites the propellant grain. Aboo-ster pellet 67 is positioned inside the forward end of thepropellant grain, the composition of which is disclosed in thepreviously referenced patent application. Quickmatch 68 which is simplyblack powder and cotton string is positioned forward of the nozzleinside the casing adjacent the nozzle ports. Then the first fire waterproof primary igniter is provided by using a standard empty pistolcartridge 69 with a primer 71 located in the center thereof. This coversthe rearward end of the casing with a water tight press fit in order tokeep the water out. The combination of the cartridge cap and thebooster, as second tire igniter, solves the problem of using rocketsunderwater since the nozzle orifices must be covered or plugged untilthe propellant is lighted and then immediately uncovered ta permit theescape of the eom busion gases. This arrangement of the cartridge capand second fire igniter solves other problems attendant to miniaturerockets, such as the phenomena of ignition spike. When the miniaturerockets are ignited they sometimes experience this phenomena wherebythey produce a burst of thrust due to partial ignition and then themotor loses thrust for a short period until complete ignition issubsequently achieved. Sometimes the ignition spike is sufficient topropel the rockets out of the launcher, but is not sufficient to sustainthe rocket in a state of stability during the period of reduced thrust.One method of overcoming this problem involves restraining the rocketuntil it is properly ignited. The friction fit of the cartridge cap onthe rear of the rocket performs the restraining function until therocket motor thrusts the rocket out of the cartridge. Thus by using thisarrangement the rocket motor can be ignited by the simple firing pinmechanism common to most firearms and yet is and remains watertightuntil the rocket motor is properly ignited, while also restraining therocket until the motor is properly thrusting. This unique combinationmakes miniature rockets of the present invention practicable forunderwater use for the first time.

When a high explosive warhead is used on the front end of the rocket, adetonator delay fusing means can be disposed between the warhead and thepropellant grain and comprises a pyrotechinc filled tubular metal delayelement 72. This element is standard delay fusing obtainable fromAmerican Cyanamid Co. (similar to that used in delay blasting caps).Alternatively, impact detonator means can be employed as will behereinafter described in connection with FIGURE 6.

When using a delay fusing technique, a layer or section of delay mix 73such as boron, fbarium chromate (BBaCrO is located behind or rearwardlyadjacent the delay mix and forwardly adjacent the propellant grain andthe booster pellet, i.e., the bulkhead is sandwiched bet-ween the activeportion of the delay element and the propellant elements contained inthe combusition chamber of the rocket. The bulkhead is formed forpermitting the transmission of heat or flame from the booster or theburning propellant of the combustion chamber to the delay mix, whilepreventing it from passing rearwardly through the bulkhead and into thecombustion chamber during the acceleration of the rocket and the burningof the propellant grain. This is accomplished by forming the bulkhead ofa metal disc and punching or piercing the hole or port of perforationtherethrough. The punching or piercing process is performed in such amanner as to leave a flap 76 or overlapping projection formed by themetal displaced by the punching or piercing operation covering theperforation 77. This structural arrangement thereby obstructs thestraight line flow path and creates a semi-efiective unidirectionalvalve which permits the burning propellant to ignite the delay fusingtrain but prevents it from being blown out the rearward end of therocket. The rockets are designed so that when fully assembled they havea center of gravity (CG) at least 60% of the length of the rocket fromthe rear end and as far forward as possible to achieve lancestabilization. The rotational moment imparted to the rocket from thenozzle means prevents excessive dispersion of the rockets from theintended target. The finless rockets are utilized to achieve a smal-ledweapon design and to eliminate external projections which might bedamaged in the rough handling that an underwater hand weapon mustgenerally be able to withstand.

In operation, the firing sequence progresses through the steps of havinga firing pin strike the primer cap located in the cartridge caseattached or secured to the rear of the rocket. The primer ignites aflash sensitive mix which can be painted in the nozzle ports andtransmits the heat to the quiclematch element. The flash mix is not anecessary element but insures ignition. The quickmatch in turn transmitsheat by deflagration, radiation and/or other means to the boosterigniter pellet in the forward end of the performation to ignite theforward end of the propellant grain. The burining of the booster and thepropellant grain ignites the delay mix, which is part of the delaytrain, and subsequently the delay element. After the delay element hasburned the length of the tube it detonates the warhead explosive. Thetime delay element is selected to permit the rocket time to traverse thetrajectory and to penetrate the target, and yet detonate shortlythereafter to prevent the target, it a fish, from swimming away or beingkilled.

FIGURE 3 of the drawings shows the nozzle of the embodiment of FIGURE 2through plane 33.

The nozzle 66 imparts a moment of angular rotation to the rocket bodyabout its longitudinal axis. In order to achieve this effect the nozzleis provided with four skewed ports 78. Any number greater than two aresuitable. The orifices are arranged in a quasi helical fashion wherebythe ports are canted with respect to the longitudinal axis of the rocketwith the axis of flow having an effective thrust vector componentperpendicular to a radius of chamber cross section. Holes are made witha tapering diameter from small at the inner end to large at the exit oraft end, thereby forming a diverging nozzle cone. A converging-divergingnozzle port could be formed by counter tapering the holes. The gasesissuing from the ports exert a twisting force component on the nozzlethereby imparting the rotation of the rocket casing.

It can be seen from this view how the nozzles are canted. By using theroll stabilization provided by this nozzle the dynamic performance ofthe missile and the dispersion reduction characteristics are greatlyimproved. Roll stabilization obviates the necessity for using fins toachieve rocket accuracy. While not being absolutely essential, rollstalbalization is effective in reducing dispersion by continuouslyorienting the rocket about a mean trajectory path rather than permittingany dispersion causing imbalance to permit the rocket to continue on adiverging track from the intended trajectory. Rockets which are not rollstabilized but Which have a high length to diameter ratio, and aseparation of their center of gravity and center of pressure (center ofpressure being aft of the center of gravity), are also stable. Theunderwater rockets of the present invention are designed to inherentlyinclude this latter described par-ameter and therefore exhibitstabilization without roll, but combining the two means of stabilizationprovides a further degree of accuracy. Thus by using the nozzledescribed, it may be seen that the gases egressing from the nozzle portswill have some of their linear momentum converted into an angularrotational moment causing the rocket to slowly roll about itslongitudinal axis. Alternate methods of achieving roll stabilization areshown herein below and described in greater detail. Other types of rollstabilization nozzles and configurations can be seen from US. patentapplication entitled Miniature Ballistic Rocket, Ser. No. 445,276, filedApr. 2, 1965.

FIGURE 4 shows a form of the invention wherein a standard pointed spear79 is driven by rocket propulsion consistent with the teachings of thepresent invention. This rocket has an outer casing 81 which is a singlepiece made of Bundy lap-Welded seamless tubing. This tubing has a veryhigh bursting strength and yet is a very economical type of tubing costwise. In practice, any high strength tubing can be used. The case isformed by selecting a piece of tubing the length of the rocket and thenmetal forming the nose end 82 into a closed section. The interiorportion 83 of the forward end of the casing is then filled with weightsuch as compacted shot, extruded rod, or simply molten lead, or someother low temperature melting metal having a high density, which willprovide a weighted nose to the rocket. If compacted shot is used forweighting, then a fire wall should be secured rearward of the shot toprevent the gases of combustion from the rocket motor penetratingforward into the casing, thereby absorbing energy. If lead or some otherheavy metal is poured into the forward end of the rocket a sealed firewall is formed naturally at the rear surface thereof, and anindividually positioned fire wall can be dispensed with. This weightednose provides the proper balance to the rocket and lends interiorrigidity to the casing to provide a strong spear. A rocket motor is usedsimilar to that of the embodiment of FIGURE 2, but an alternativeignition means is used. A fuse 84 or igniter extends the length of thepropellant grain 86 to the booster 87 at the forward end of the grain.The igniter can be a piece of porous paper coated by spraying or dippingwith a mixture of 2A and nitrocellulose. 2A'is a common rocket igniterconsisting of 20% amorphous boron and potassium nitrate, 50 parts byweight of 2A is used with 1 part of Du Pont cotton base nitro-cellulose.Acetone serves as a solvent during dipping or spraying. Substitution ofblack rifle powder for the 2A '7 is satisfactory. The booster pellet canbe dispensed with if this igniter is used instead of quickmatch in thenozzle. The nozzle is formed directly in the casing by simply rolling orcrimping a reduced diameter section into the exterior wall of the rocketcasing, and the angular Iotational means is formed in the portion of thenozzle cone rearward of the annular groove by a simple stampingoperation. Slits are cut longitudinally into the casing wall and thevanes bent down into the exit portion of the nozzle to deflect the gasesexhausting therethrough, thereby imparting the angular rotation of therocket. This is a relatively inexpensive way to form a rocket. Anigniter cap is sealed to the rear end of the rockets surface by afriction fit as in the embodiment of FIGURE 2. When the primer is firedthe igniter uniformly lights the propellant grain longitudinally alongthe perforation.

FIGURE is a projection of the nozzle of FIGURE 4 through plane 55. Itcan be seen how the vanes 88 are positioned in the path of the gas flowemerging from the nozzle and exhausting through the nozzle cone.

FIGURE 6 is an embodiment of the invention providing an impactdetonating mechanism for a warhead carrying underwater rocket. A nose 89of metal is formed or mechanically connected to a casing 91 and forms aforward bulkhead 92 to support an impact detonating fuse means 93. Inthis instance a simple impact detonator is use-d which is produced bythe Cap-Chur Co., of Atlanta, Ga. Rearward of the detonating means isthe warhead 94 which is exploded by the detonating means which isactivated upon impact with a target. Rearward of the warhead is a firewall 96 which is crimped into the casing providing a bulkhead for therocket propulsion motor similar to that described in FIGURE 4.

FIGURE 7 shows a warhead for use with the rockets of the presentinvention. Because of the new and novel results effected by theseweapons when used as an underwater weapon, these weapons have suchpenetrating power,

as compared with the weapons of the prior art, that different warheadconfigurations are considered desirable for use therewith. Generally anunderwater spear is constructed for the purpose of penetrating thetar-get and then engaging it to prevent it from being withdrawn. Barbednoses or similar type configurations are used to prevent a fish fromshaking the spear out or having it pull free. The weapon of the presentinvention strikes with such force that it would very possibly passcompletely through a fish. Therefore provision is made to insure thatthe rocket driven spear stays in the fish and delivers all of its energyof impact to the target. This is accomplished by providing a nose 97with longitudinal striated sections 98 and a notched area 99, such asthe neck of an arrow. Thus when the nose portion strikes the fish thenose splits and separates into sections along the striation lines andmushrooms. This internally ruptures the fish and creates the largerfrontal area to the rocket nose which insures that the rocket does notcompletely pass through the fish.

In FIGURE 8 a simple arrangement is shown whereby the rockets of thepresent invention can be combined with presently existing equipment forconstructing a simple, inexpensive underwater hand gun. An underwatermilitary demolition lighter fuse 101 Model M2 is adapted to a simplefiring tube 102 containing a rocket 103 of the present invention. Thefiring tube is approximately the length of the rocket and has a rearwardflange 104 for providing a seat for the fuse pin body and a threadedrear portion to engage the portion of the fuse which is to be used inthis embodiment. The rocket is restrained in the launcher by means ofthe cartridge cap 106 on the rear end of the rocket. A firing pin 107 isheld in cocked position, wherein the spring 108 is compressed, by meansof a locking pin 109 through the shank of the firing pin. A ring 111 isprovided to permit easy removal of the locking pin from the firing pinwhereby it is snapped forward into the primer in the cartridge cap onthe rocket. This type of weapon arrangement could be used as a one shotdevice for self defense. In order to use this device as a reloadablereusable mechanism, only slight modifications are necessary as shown inFIGURE 9. The rear end of fuse body portion could be threaded and asimple handle 112 added thereto whereby the firing pin 113 could bereturned to the cocked position. The handle is provided with alongitudinal slot 114 permitting access by the finger of the operator togrip the firing pin and recompress the firing spring. When the firingpin 113 has been returned to its cocked position and the spring onceagain compressed, the lockpin may be reinserted in an appropriateperforation in the shank portion of the firing pin such as shown inFIGS. 9 and 10 and as previously described in connection with the typeof weapon shown in FIG. 8. The handle 112 also permits simple operationprocedures, such as reloading and recockin-g the weapon under water.

FIGURE 11 depicts an alternate nozzle means for roll stabilization ofthe rocket. This nozzle is produced by taking a piece of solid rod,having a polygonal cross section, preferably triangular, and twisting itto the desired helical degree. A piece of the twisted rod 123 theninserted and secured into the rocket casing 124 rearwardly of thepropellant grain 126 and in spaced relation thereto. This causes aconstricting cross section in the exit portion 127 (FIGURE 12) of thecasing through which the gases of combustion exhaust. The constrictingeffect results in providing a nozzle for the rocket. As the gases ofcombustion egress through this portion of the casing, the helicalconfiguration of the twisted rod causes the gases to flow in such amanner that the linear momentum thereof is partially converted toinclude an angular moment which causes the rocket to rotate around thelongitudinal axis.

The propellant is restrained in the forward end of the combustionchamber by metal tabs 128 from the interior wall of the casing formed bya breaching tool. As with the devices of the previous embodiments,primer cap ignition is also provided which consists of an emptycartridge cap 129 coaxially pressure fitted t0 the rear end of thecasing and including a primer cap 131 which is disposed in a seat at therear of the cap and provided with a communication port 132 to theinterior of the rocket. An igniter fuze 133 extends the length of theperforation and through a hole 134 in the twisted rod. Alternatively,the igniter could be run around the sides of the twisted rod, betweenthe rod and the casing wall, thereby eliminating a hole through thecenter of the rod. Alternatively, a flash mix material could be disposedon the surfaces of the rod before it is inserted into the casing, whichtransmits the heat of ignition from the primer cap to the igniter fuse.

FIGURE 12 is an end view taken on line 12-12 of FIGURE 11 showing howthe piece of twisted rod is restrained in the casing by means of theflange 136 which is rolled into the rear end of the rocket casingsecuring the rod therein. A sophisticated version of this embodimentwould permit use of the 4 or 5 or 6 sided rod whereby very smallclearances are then provided between the wall of the casing and the rod.In this embodiment, a nozzle would then be formed down the center of therod with a diverging exit cone or a convergingdiverging orifice. Thiscould simply be done by drilling and .counterboring. With thisarrangement a basic portion of the exhaust gases would be properlyconstricted for egress through the portion of the rod while only thesmall portion of the issuing gases would be diverted to escape aroundthe outside of the rod between the casing wall and the rod surfaces.This would permit the basic or the largest portion of the exhaust gasesto be used for propelling the rocket and the siphoning off only asmaller percentage of the exhausting gases for providing the angularrotation.

FIGURE 13 is a further alternate nozzle means for providing rollstabilization to the rocket. In this embodiment the skewed vanes 137 arepositioned in the rocket nozzle forward of the constricted orifice 138.This is achieved by providing an insert 139 for the rocket casing whichhas a configuration comparable to a spiral miter gear. The insert tapersto conform to the converging portion of the nozzle cone. The spiralteeth on the insert provide the skewed vanes which divert the gases ofcombustion exhausting through the nozzle to create the angular moment.The nozzle throat is created by metal forming the nozzle casing over theinsert and then metal forming a comparable diverging portion 141 to thecasing whereby a converging-diverging nozzle cross section is formed inthe rocket casing. Similarly, as with the embodiment of FIGURE 11 acentral perforation could be provided in the insert to permit exhaustionof a basic portion of the gases of combustion whereby only a smallerportion is siphoned off to provide the angular turning moment. Theskewedness ofthe vanes can range from one to approximately 35 degreesdepending upon the degree of roll stabilization desired and how much ofthe gases of combustion will be routed through the skewed vanes.Ignition of the propellant gain through this insert can be effected downthe center bore by means of an igniter fuze, if one is provided, or bymeans of an ignitor fuze routed between the vanes or by flash mixinserted on the surface of the insert between the vanes.

All of the above systems have many interchangeable arrangements ofnozzles, rocket motors and ignition means, and warheads compatible witheach other. The novel solution to the problem of waterproofing thepropellant grain and the ignition systems 'is the use of the cartridgecap as shown in the embodiments of FIGURES 2, 4, 8, 9,10, and 13.

The use of the high powered underwater rockets of the present inventionby underwater demolition teams of the Navy has the additional advantageof providing a lethal weapon which can "be used for self defense out ofthe water. The rocket provides such thrusts that the rocket 1 poweredprojectile will carry for considerable distances in air with excellentaccuracy. Thus, the UDT man does not haveto carry two types of weapons.

While changes can be made in the details of construction and methods offabrication of the underwater rockets of the present invention withoutdeparting from the spirit and scope of the invention, it is not be tolimited except as defined in the following claims.

We claim:

1. A self-contained weapon comprising an elongated lauching tube havingunobstructed forward and rear end portions, the latter being providedwith a flange means, a rocket having a casing including front and rearportions positioned in said launching tube, said casing being providedin the area of the rear portion with a nozzle means adapted to support apyrotechnic element, a pyrotechnic element mounted within said nozzlemeans, a friction type ignition means extending through said pyrotechnicelement, a warhead carried by the front portion of said casing, alongitudinally perforated propellant spaced from the ignition means andinterposed between said warhead and said nozzle means, cover meansassociated with the forward and rear end portions of said launching tubeand pull means extending through the rear cover and connected to saidignition means, whereby the relative motion between the pyrotechnicelement and said ignition means ignites said pyrotechnic element whenthe pull means is actuated.

2. A self-contained weapon as claimed in claim 1, wherein the propellantterminates in an end wall which lies continguous to a frusto-conicalrecessed area in said casing, an elongated pyrotechnic fuse in saidperforation extending from the warhead and through said perforation, andan integrated reduced area in the casing adapted to form the nozzle tocontain the pyrotechnic material, the contour of said reduced area andsaid pyrotechnic material forming a frusto-conical recess in the rearportion of said casing in opposition to said first-named frustoconicalrecess.

3. A self-contained weapon as claimed in claim 1, wherein the propellantterminates in an end wall which lies contiguous to a frusto-conica-lrecessed area in said casing, an elongated pyrotechnic fuse in saidperforation extending from the warhead and through said perforation, anozzle insert in said frusto-conical recess, said nozzle insert furtherhaving a frusto-conical .body the perimeter of which includeslongitudinally axially skewed vanes adapted to impart stabilization tothe rocket when launched.

4. A self-contained weapon as claimed in claim 1, wherein the nozzlemeans is formed integrally with the casing wall by deformation of thelatter.

5. A self-contained weapon as claimed in claim 1, wherein thelongitudinal extent of the perforated propellant is adapted to contain apyrotechnic fusing means.

6. A self-contained weapon as claimed in claim 1, wherein the rocket isadapted to be secured against inadvertent longitudinal movement in saidlaunching tube by a locking means.

7. A self-contained weapon as claimed in claim 1, wherein said covermeans associated with said front and rear portions of said casing arefrangible.

References Cited by the Examiner UNITED STATES PATENTS 2,405,415 8/ 1946Eksergian 102-49 2,824,496 2/1958 Kuller et a1 891.814 2,833,216 5/1958Rommel 10234 2,972,933 2/1961 Guthrie et al. 89l.817 3,060,854 10/1962Maretti ll420 X OTHER REFERENCES 662,429 12/1951 Great Britain.

BENJAMIN A. BORCHELT, Primary Examiner. SAMUEL w. ENGLE, Examiner,

1. A SELF-CONTAINED WEAPON COMPRISING AN ELONGATED LAUCHING TUBE HAVINGUNOBSTRUCTED FORWARD AND REAR END PORTIONS, THE LATTER BEING PROVIDEDWITH A FLANGE MEANS, A ROCKET HAVING A CASING INCLUDING FRONT AND REARPORTIONS POSITIONED IN SAID LAUNCHING TUBE, SAID CASING BEING PROVIDEDIN THE AREA OF THE REAR PORTION WITH A NOZZLE MEANS ADAPTED TO SUPPORT APYROTECHNIC ELEMENT, A PYROTECHNIC ELEMENT MOUNTED WITHIN SAID NOZZLEMEANS, A FRICTION TYPE IGNITION MEANS EXTENDING THROUGH SAID PYROTECHNICELEMENT, A WARHEAD CARRIED BY THE FRONT PORTION OF SAID CASING, ALONGITUDINALLY PERFORATED PROPELLANT SPACED FROM THE IGNITION MEANS ANDINTERPOSED BETWEEN SAID WARHEAD AND SAID NOZZLE MEANS, COVER MEANSASSOCIATED WITH THE FORWARD AND REAR END PORTIONS OF SAID LAUNCHING TUBEAND PULL MEANS EXTENDING THROUGH THE REAR COVER AND CONNECTED TO SAIDIGNITION MEANS, WHEREBY THE RELATIVE MOTION BETWEEN THE PYROTECHNICELEMENT AND SAID IGNITION MEANS IGNITES SAID PYROTECHNIC ELEMENT WHENTHE PULL MEANS IS ACTUATED.